CA2550146A1 - Bendable wing for micro air vehicle - Google Patents
Bendable wing for micro air vehicle Download PDFInfo
- Publication number
- CA2550146A1 CA2550146A1 CA002550146A CA2550146A CA2550146A1 CA 2550146 A1 CA2550146 A1 CA 2550146A1 CA 002550146 A CA002550146 A CA 002550146A CA 2550146 A CA2550146 A CA 2550146A CA 2550146 A1 CA2550146 A1 CA 2550146A1
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- Prior art keywords
- wing
- micro air
- air vehicle
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- inches
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- 229920000049 Carbon (fiber) Polymers 0.000 claims description 5
- 229920006231 aramid fiber Polymers 0.000 claims description 5
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- 239000004744 fabric Substances 0.000 claims description 4
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- 239000004760 aramid Substances 0.000 claims description 3
- 229920003235 aromatic polyamide Polymers 0.000 claims description 3
- 229910052799 carbon Inorganic materials 0.000 claims description 3
- 239000004918 carbon fiber reinforced polymer Substances 0.000 claims description 3
- 239000006261 foam material Substances 0.000 claims description 3
- 239000011521 glass Substances 0.000 claims description 3
- 239000004816 latex Substances 0.000 claims description 3
- 229920000126 latex Polymers 0.000 claims description 3
- 239000004033 plastic Substances 0.000 claims description 3
- 229920003023 plastic Polymers 0.000 claims description 3
- 239000010935 stainless steel Substances 0.000 claims description 3
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Classifications
-
- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H27/00—Toy aircraft; Other flying toys
- A63H27/007—Collapsible wings, e.g. for catapult aeroplanes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
- B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/11—Propulsion using internal combustion piston engines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/20—Launching, take-off or landing arrangements for releasing or capturing UAVs in flight by another aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/12—Propulsion using turbine engines, e.g. turbojets or turbofans
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U80/00—Transport or storage specially adapted for UAVs
- B64U80/70—Transport or storage specially adapted for UAVs in containers
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
- Fittings On The Vehicle Exterior For Carrying Loads, And Devices For Holding Or Mounting Articles (AREA)
Abstract
A micro air vehicle (10) having a bendable wing (12) enabling the micro air vehicle to fly. The bendable wing (12) may be bent downwards so that the wingspan may be reduced for storing the micro air vehicle. The bendable wing (12) may be formed from one or more layers of material (22), and the wing may have a camber such that a concave surface of the wing faces downward. The wing may substantially resist flexing upwards and may transfer uplift forces to a central body of the micro air vehicle (10). In addition, the wing may be bent severely downwards by applying a force to tips (13) of the wing. The micro air vehicle is capable of being stored in a small cylindrical tube and may be deployed from the tube by simply releasing the micro air vehicle from the tube.
Description
BENDABLE~ WING FOR MICRO AIR VEHICLE
CROSS-REFERENCE TO RELATED APPLICATION
S
This application claims the benefit of U.S. Provisional Application No.
60/431,920, filed December 9, 2002.
FIELD OF THE INVENTION
This invention is directed generally to micro air vehicles, and more particularly, to wing configurations for micro air vehicles.
BACKGROUND
Micro air vehicles can trace their beginnings to model airplanes, which typically 1S resemble full size airplanes. Micro air vehicles generally encompass all relatively small unmanned flying objects, such as those having wingspans less than about 36 inches. Micro air vehicles are often powered by small gasoline or electric propeller driven engines. Micro air vehicles are relatively lightweight vehicles capable of being used for a variety of purposes, such as for recreation, reconnaissance, and other purposes. Because of their small size, micro air vehicles lend themselves to a variety of uses.
Many micro air vehicles have fixed, rigid wings that are incapable of having their wing span reduced for storage. Micro air vehicles having fixed wings are often difficult to store and do not lend themselves for storage in a knapsack or other item typically carried by military personnel in reconnaissance missions. Some micro air vehicles have collapsible 2S wings that pivot about one or more pivot points. Typically, these micro air vehicles require a series of assembly steps to transform the micro air vehicle from a deployable condition to a storage condition, and vice versa.
Because of their small size and ability to go relatively unnoticed, micro air vehicles have been outfitted with cameras, both still frame cameras and video cameras, and used in hostile areas for reconnaissance purposes. However, many of the micro air vehicles are inconvenient to be carried by military personnel because of their cumbersome wing span and shape. Thus, a need exists for a micro air vehicle having wings capable of having their wingspan reduced. In addition, other micro air vehicles having wings with reduceable wingspans require a plurality of assembly steps to transform the wings of the micro air vehicle from a deployable condition to a storage condition, and vice versa.
Such requirements prevent these micro air vehicles from being deployed quickly and without human interaction. If micro air vehicles were able to be transformed between a storage condition and a deployable condition without assembly steps, the micro air vehicles could be used in a greater variety of applications. Thus, a need exists for a micro air vehicle capable of being transformed between a storage condition and a deployable condition without assembly steps.
SUMMARY OF THE INVENTION
This invention is directed to a micro air vehicle having a bendable wing enabling the micro air vehicle to be stored in containers substantially smaller than the micro air vehicle and enabling the bendable wing to go from a storage condition to a deployable condition without assembly or user interaction. Rather, the forces used to hold the wing tips of the wing need only be abated.
CROSS-REFERENCE TO RELATED APPLICATION
S
This application claims the benefit of U.S. Provisional Application No.
60/431,920, filed December 9, 2002.
FIELD OF THE INVENTION
This invention is directed generally to micro air vehicles, and more particularly, to wing configurations for micro air vehicles.
BACKGROUND
Micro air vehicles can trace their beginnings to model airplanes, which typically 1S resemble full size airplanes. Micro air vehicles generally encompass all relatively small unmanned flying objects, such as those having wingspans less than about 36 inches. Micro air vehicles are often powered by small gasoline or electric propeller driven engines. Micro air vehicles are relatively lightweight vehicles capable of being used for a variety of purposes, such as for recreation, reconnaissance, and other purposes. Because of their small size, micro air vehicles lend themselves to a variety of uses.
Many micro air vehicles have fixed, rigid wings that are incapable of having their wing span reduced for storage. Micro air vehicles having fixed wings are often difficult to store and do not lend themselves for storage in a knapsack or other item typically carried by military personnel in reconnaissance missions. Some micro air vehicles have collapsible 2S wings that pivot about one or more pivot points. Typically, these micro air vehicles require a series of assembly steps to transform the micro air vehicle from a deployable condition to a storage condition, and vice versa.
Because of their small size and ability to go relatively unnoticed, micro air vehicles have been outfitted with cameras, both still frame cameras and video cameras, and used in hostile areas for reconnaissance purposes. However, many of the micro air vehicles are inconvenient to be carried by military personnel because of their cumbersome wing span and shape. Thus, a need exists for a micro air vehicle having wings capable of having their wingspan reduced. In addition, other micro air vehicles having wings with reduceable wingspans require a plurality of assembly steps to transform the wings of the micro air vehicle from a deployable condition to a storage condition, and vice versa.
Such requirements prevent these micro air vehicles from being deployed quickly and without human interaction. If micro air vehicles were able to be transformed between a storage condition and a deployable condition without assembly steps, the micro air vehicles could be used in a greater variety of applications. Thus, a need exists for a micro air vehicle capable of being transformed between a storage condition and a deployable condition without assembly steps.
SUMMARY OF THE INVENTION
This invention is directed to a micro air vehicle having a bendable wing enabling the micro air vehicle to be stored in containers substantially smaller than the micro air vehicle and enabling the bendable wing to go from a storage condition to a deployable condition without assembly or user interaction. Rather, the forces used to hold the wing tips of the wing need only be abated.
The micro air vehicle may be formed from a central body and one or more wings.
The wing may be formed from one or more layers of a resilient material having a camber forming a concave surface facing downward. The wing may be bendable from a steady state position in a first direction such that tips of the wing may be bent toward the concave surface but not in a second direction that is generally opposite to the first direction. In other words, the wing may bent downwards but not upwards. The wing may also be capable of returning to the steady state position upon release the tips of the wing.
The wing may have a camber such that a bottom surface of the wing has a generally concave configuration when viewed parallel to a longitudinal axis of the wing.
The camber may contribute to the stability of flight of a micro air vehicle to which the wing is attached and allow the wing to be bent downwards by not upwards. Thus, the wing may absorb and transfer uplift forces to the central body and allow the wing to be bent downward for storage.
In an alternative embodiment, the wing may be formed from a support structure covered by a layer of material. The support structure may be formed from one or more ribs, which may be, but are not required to be, generally parallel to each other.
The layer of material covering the support structure may be, but is not limited to being, latex or other appropriate materials.
The bendable wing enables the wing to be stored is containers smaller than the micro air vehicle to which the wing is attached. For instance, the bendable wing having a wing span of about ten inches may be bent around the central body of a micro air vehicle so that the wing may be stored in a container having a diameter of about three inches.
Such a characteristic enables a micro air vehicle to which the bendable wing is attached to be used for reconnaissance missions, for deployment from missiles just prior to impact for bomb damage assessment, and carried by special forces operatives in the field on their person.
An advantage of this invention is that a micro air vehicle incorporating the bendable wing of this invention may be stored in a small container and deployed without any actions taken to assemble the wings other than to release the tips from restraint.
Releasing the wings enables the wings to return to the steady state position.
Another advantage of this invention is that the bendable wing has sufficient stiffness to absorb and transfer uplift forces to the body wlule enabling the wings to be bent downwardly for storage.
Yet another advantage of this invention is that by being able to be stored in such a small container, a micro air vehicle may be conveuently carried on a person, such as military personnel, without consuming much room.
Still another advantage of this invention is that the bendable wing may be produced relatively inexpensively.
Another advantage of this invention is that the wing is durable and capable of withstanding crash landings.
These and other advantages will become obvious upon review of the detailed written description below of these and other embodiments.
BRIEF DESCRIPTION OF THE DRAWINGS
The accompanying drawings, which are incorporated in and form a part of the specification, illustrate preferred embodiments of the presently disclosed inventions) and, together with the description, disclose the principles of the invention(s).
These several illustrative figures include the following:
Figure 1 is a perspective view of a top side of an embodiment of this invention;
Figure 2 is a perspective view of the embodiment shown in Figure 1 with a portion of the bendable wing being bent around a central body of a micro air vehicle as a result of a downward force applied to a tip of the wing;
Figure 3 is a front view of a micro air vehicle inserted into a small diameter tube with both sides of the bendable wing bent around the central body of the micro air vehicle;
Figure 4 is a perspective view of an alternative embodiment of the bendable wing of the micro air vehicle;
Figure 5 is a perspective view of the alternative embodiment of the bendable wing shown in Figure 4 in flexed storage condition with the tips of the wing bent around the central body of the micro air vehicle;
Figure 6 is a perspective view of yet another alternative configuration of the bendable wing of this invention;
Figure 7 is a front view of the embodiment shown in Figure 6;
Figure 8 is a perspective view of still another embodiment of this invention;
Figure 9 is a front view of another embodiment of this invention; and Figure 10 is a perspective view of a top side of the embodiment shown in Figure 9.
DETAILED DESCRIPTION OF THE INVENTION
This invention is directed to a wing 12 for a micro air vehicle 10, as shown in Figures 1-10, that is bendable to enable the wing 12 to be easily stored in, for instance, a tube or other structure. The.wing 12 may be attached to a body 14 that may or may not house an engine capable of providing rotational motion to a propeller 16. The engine may be, but is not limited to, one of many conventional engines used to power miniature aircraft. Body 14 may include a tail 17 for controlling the micro air vehicle 10. The tail 17 may be positioned generally orthogonal to the wing 12, as shown in Figures l, 2, 8, and 10, generally parallel to the wing 12, as shown in Figures 4 and 5, or in another position. Micro air vehicle 10 may include other components that are typically found on miniature aircraft.
As shown in Figures 4 and 5, wing 12 may be formed one or more layers formed from resilient materials such that the wing 12 is bendable from a steady state position. The wing 12 may be bent in a first direction, as shown in Figure S, such that tips 13 of the wing 12 may be bent downwardly toward a concave surface 15 but not substantially in a second direction that is generally opposite to the first direction. The resilient materials have a high degree of elasticity and are therefore capable of returning the wing 12 to the steady state position upon release of the tips 13 of the wing 12. In at least one embodiment, the camber of the wing 12 is configured such that a bottom surface of the wing 12 forms a concave surface.
Wing 12, as shown in Figures 1, 4, 6, and 8, may be formed from a leading edge portion 18, a rear portion 19, and a trailing edge 25. Leading edge portion 18, rear portion 19, and trailing edge 25 may together form a monolithic structure formed from the same material, or may be different structures formed from the same or different materials and coupled together. In at least one embodiment, the wing 12, as shown in Figure 4, may be formed from a single layer of material, and, in alternative embodiments, may be formed from two or more layers of material. The wing 12 may be formed from resilient materials, such as, but not limited to: fiber reinforced laminates and fabrics, such as, carbon fiber reinforced polymers, glass reinforced polymers, and aramid reinforced polymers; sheet metal, such as, spring steel, high strength aluminum, stainless steel, and titanium; foam materials; and plastics. In at least one embodiment, leading edge portion 18 may be formed from pre-impregnated carbon/epoxy fiber cloth, which provides sufficient strength to absorb forces encountered from wind gusts while maintaining a sufficiently light weight. In at least another embodiment, the leading edge 18 may be formed from an aramid fiber/epoxy mixture and at least a portion of the remainder of the rear portion 19 may be formed from a single layer of carbon fiber/epoxy weave.
Wing 12 is bendable so that the overall size of micro air vehicle 10 may be reduced for storage. Wing 12 may be bent by applying a downward force to the tips 13 of wing 12, as shown in Figures 2 and 5. While wing 21 may be bent downwards, wing 12 resists being bent upwardly as a result of the camber of leading edge portion 18 or the wing 12, or both.
More specifically, the leading edge portion 18 is stiff when loaded with upwardly directed loads, such as aerodynamic loads. The camber provides wing 12 with the structural stability to substantially prevent wing 12 from bending upwardly when subjected to an upwardly directed load. Thus, wing 12 can be bent with a downwardly applied force but not with an upwardly applied force because of the configuration of the wing 12 and materials used to form the wing 12. The wing 12 may be bent so that a substantial portion of the wing 12 may be wrapped around to an opposite side of the body 14 from the steady state position shown in Figures 1 and 5.
In other embodiments, as shown in Figures 1, 2, and 6-10, rear portion 19 may be formed from ribs 20 and a skin 22. Ribs 20 may be formed from unidirectional fibers, such as, but not limited to, carbon fiber strands, and skin 22 may be formed from a lightweight, thin material, such ash but not limited to, latex and other appropriate materials. Ribs 20 may include members positioned generally parallel to body 14.
Rear portion 19 may or may not be concave when viewed from below, as shown in Figure 10. If rear portion 19 is concave, the concave shape of rear portion 19 may or may not be equal to the concave shape of leading edge portion 18. If the rear portion 19 is not concave, the leading edge portion 18 has a camber forming a concave face on the bottom surface 1 S of the wing 12. The shape of rear portion 19 may be any shape capable of providing aerodynamic lift when coupled to leading edge portion 18. Rear portion 19 may include a riser 21 at the rear portion of wing 12. The riser 21 may form a concave portion on an upper surface 23 of the wing 12 in the rear portion 19. The riser 21 may extend completely across the trailing edge 25 or may extend across only a portion of the trailing edge 25.
In one embodiment, leading edge 18 has a greater thickness than the thickness of the rear portion 19, wherein the characteristic that wing 12 may be bent downwards but not upwards is attributable to the configuration of leading edge portion 18. In other embodiments, leading edge portion 18 and reax portion 19 may or may not have the same thickness, depending on the strength of the materials used to form leading edge portion 18 and rear portion 19.
Wing 12 may have a wing span between about six inches and about twenty four inches. In one embodiment, wing 12 may have a ten inch wing span enabling it to be stored in a cylinder 24, as shown in Figure 3, having a diameter less than three inches. Having the capability of being stored in such small cylinders enables micro air vehicle 10 to be used for reconnaissance missions, for deployment from missiles just prior to impact for bomb damage assessment, and carried by special forces operatives in the field on their person. Micro-air vehicle 10 may be used in other applications as well. In other embodiments, wing 12 may vary in length between about three inches and about 24 inches. As shown in Figures 7 and 9, the micro air vehicle 10 may include a camera 30, wluch may be, but is not limited to being, a video camera, a still photography camera, or other audio or visual recording devices.
The configuration of wing 12 shown in Figures 1-10 and the elastic materials from which the wing 12 is formed enables wing 12 to return to its original, steady state shape, as shown in Figure 1, 4, and 6-10, after being removed from storage without additional steps or use of mechanical mechanisms, such as servos, motors, piezoelectrics, or shape memory alloys. Instead, wing 12 returns to its original shape because of the elastic characteristics of the wing 12 causes the wing 12 to remain under forces when bent from its original position.
These forces abate only when wing 12 is returned to its original position. The materials used to form the wing 12 have great flexibility and elasticity and bend rather than permanently yielding. Thus, micro air vehicle 10 needs only to be removed from a storage container 24, as shown in Figure 3, for wing 12 to return to its original shape.
The wing 12 is configured such that the wing 12 may be bent severely about the body 14 of the micro air vehicle 10. In fact, the wing 12 may be bent so severely that the wing tips 13 and wing 12 are rolled up around the body 14, as shown in Figure 5. This configuration is very advantageous. However, the wing 12 also prevents substantial bending in the opposite direction. This is not to say that the wing will not flex during use. Rather, the wing 12 will flex, or bow, in the opposite direction under normal stresses associated with flight. However, the wing 12 will not bend substantially in the opposite direction.
The configuration of wing 12 possess numerous aerodynamic advantages including:
reduced drag due to the curvature of leading edge portion 18; and improved wind gust rejection due to adaptive washout as a result of wing 12 flexing, twisting and decambering.
This configuration of wing 12 allows micro air vehicle 12 to fly more smoothly than conventional rigid wing designs in smooth and gusty wind conditions. Wing 12 is also more durable than rigid wings because the configuration of wing 12 bends upon impact with the ground or other structure, rather than breaking.
The foregoing is provided for purposes of illustrating, explaining, and describing embodiments of this invention. Modifications and adaptations to these embodiments will be apparent to those skilled in the art and may be made without departing from the scope or spirit of this invention.
The wing may be formed from one or more layers of a resilient material having a camber forming a concave surface facing downward. The wing may be bendable from a steady state position in a first direction such that tips of the wing may be bent toward the concave surface but not in a second direction that is generally opposite to the first direction. In other words, the wing may bent downwards but not upwards. The wing may also be capable of returning to the steady state position upon release the tips of the wing.
The wing may have a camber such that a bottom surface of the wing has a generally concave configuration when viewed parallel to a longitudinal axis of the wing.
The camber may contribute to the stability of flight of a micro air vehicle to which the wing is attached and allow the wing to be bent downwards by not upwards. Thus, the wing may absorb and transfer uplift forces to the central body and allow the wing to be bent downward for storage.
In an alternative embodiment, the wing may be formed from a support structure covered by a layer of material. The support structure may be formed from one or more ribs, which may be, but are not required to be, generally parallel to each other.
The layer of material covering the support structure may be, but is not limited to being, latex or other appropriate materials.
The bendable wing enables the wing to be stored is containers smaller than the micro air vehicle to which the wing is attached. For instance, the bendable wing having a wing span of about ten inches may be bent around the central body of a micro air vehicle so that the wing may be stored in a container having a diameter of about three inches.
Such a characteristic enables a micro air vehicle to which the bendable wing is attached to be used for reconnaissance missions, for deployment from missiles just prior to impact for bomb damage assessment, and carried by special forces operatives in the field on their person.
An advantage of this invention is that a micro air vehicle incorporating the bendable wing of this invention may be stored in a small container and deployed without any actions taken to assemble the wings other than to release the tips from restraint.
Releasing the wings enables the wings to return to the steady state position.
Another advantage of this invention is that the bendable wing has sufficient stiffness to absorb and transfer uplift forces to the body wlule enabling the wings to be bent downwardly for storage.
Yet another advantage of this invention is that by being able to be stored in such a small container, a micro air vehicle may be conveuently carried on a person, such as military personnel, without consuming much room.
Still another advantage of this invention is that the bendable wing may be produced relatively inexpensively.
Another advantage of this invention is that the wing is durable and capable of withstanding crash landings.
These and other advantages will become obvious upon review of the detailed written description below of these and other embodiments.
BRIEF DESCRIPTION OF THE DRAWINGS
The accompanying drawings, which are incorporated in and form a part of the specification, illustrate preferred embodiments of the presently disclosed inventions) and, together with the description, disclose the principles of the invention(s).
These several illustrative figures include the following:
Figure 1 is a perspective view of a top side of an embodiment of this invention;
Figure 2 is a perspective view of the embodiment shown in Figure 1 with a portion of the bendable wing being bent around a central body of a micro air vehicle as a result of a downward force applied to a tip of the wing;
Figure 3 is a front view of a micro air vehicle inserted into a small diameter tube with both sides of the bendable wing bent around the central body of the micro air vehicle;
Figure 4 is a perspective view of an alternative embodiment of the bendable wing of the micro air vehicle;
Figure 5 is a perspective view of the alternative embodiment of the bendable wing shown in Figure 4 in flexed storage condition with the tips of the wing bent around the central body of the micro air vehicle;
Figure 6 is a perspective view of yet another alternative configuration of the bendable wing of this invention;
Figure 7 is a front view of the embodiment shown in Figure 6;
Figure 8 is a perspective view of still another embodiment of this invention;
Figure 9 is a front view of another embodiment of this invention; and Figure 10 is a perspective view of a top side of the embodiment shown in Figure 9.
DETAILED DESCRIPTION OF THE INVENTION
This invention is directed to a wing 12 for a micro air vehicle 10, as shown in Figures 1-10, that is bendable to enable the wing 12 to be easily stored in, for instance, a tube or other structure. The.wing 12 may be attached to a body 14 that may or may not house an engine capable of providing rotational motion to a propeller 16. The engine may be, but is not limited to, one of many conventional engines used to power miniature aircraft. Body 14 may include a tail 17 for controlling the micro air vehicle 10. The tail 17 may be positioned generally orthogonal to the wing 12, as shown in Figures l, 2, 8, and 10, generally parallel to the wing 12, as shown in Figures 4 and 5, or in another position. Micro air vehicle 10 may include other components that are typically found on miniature aircraft.
As shown in Figures 4 and 5, wing 12 may be formed one or more layers formed from resilient materials such that the wing 12 is bendable from a steady state position. The wing 12 may be bent in a first direction, as shown in Figure S, such that tips 13 of the wing 12 may be bent downwardly toward a concave surface 15 but not substantially in a second direction that is generally opposite to the first direction. The resilient materials have a high degree of elasticity and are therefore capable of returning the wing 12 to the steady state position upon release of the tips 13 of the wing 12. In at least one embodiment, the camber of the wing 12 is configured such that a bottom surface of the wing 12 forms a concave surface.
Wing 12, as shown in Figures 1, 4, 6, and 8, may be formed from a leading edge portion 18, a rear portion 19, and a trailing edge 25. Leading edge portion 18, rear portion 19, and trailing edge 25 may together form a monolithic structure formed from the same material, or may be different structures formed from the same or different materials and coupled together. In at least one embodiment, the wing 12, as shown in Figure 4, may be formed from a single layer of material, and, in alternative embodiments, may be formed from two or more layers of material. The wing 12 may be formed from resilient materials, such as, but not limited to: fiber reinforced laminates and fabrics, such as, carbon fiber reinforced polymers, glass reinforced polymers, and aramid reinforced polymers; sheet metal, such as, spring steel, high strength aluminum, stainless steel, and titanium; foam materials; and plastics. In at least one embodiment, leading edge portion 18 may be formed from pre-impregnated carbon/epoxy fiber cloth, which provides sufficient strength to absorb forces encountered from wind gusts while maintaining a sufficiently light weight. In at least another embodiment, the leading edge 18 may be formed from an aramid fiber/epoxy mixture and at least a portion of the remainder of the rear portion 19 may be formed from a single layer of carbon fiber/epoxy weave.
Wing 12 is bendable so that the overall size of micro air vehicle 10 may be reduced for storage. Wing 12 may be bent by applying a downward force to the tips 13 of wing 12, as shown in Figures 2 and 5. While wing 21 may be bent downwards, wing 12 resists being bent upwardly as a result of the camber of leading edge portion 18 or the wing 12, or both.
More specifically, the leading edge portion 18 is stiff when loaded with upwardly directed loads, such as aerodynamic loads. The camber provides wing 12 with the structural stability to substantially prevent wing 12 from bending upwardly when subjected to an upwardly directed load. Thus, wing 12 can be bent with a downwardly applied force but not with an upwardly applied force because of the configuration of the wing 12 and materials used to form the wing 12. The wing 12 may be bent so that a substantial portion of the wing 12 may be wrapped around to an opposite side of the body 14 from the steady state position shown in Figures 1 and 5.
In other embodiments, as shown in Figures 1, 2, and 6-10, rear portion 19 may be formed from ribs 20 and a skin 22. Ribs 20 may be formed from unidirectional fibers, such as, but not limited to, carbon fiber strands, and skin 22 may be formed from a lightweight, thin material, such ash but not limited to, latex and other appropriate materials. Ribs 20 may include members positioned generally parallel to body 14.
Rear portion 19 may or may not be concave when viewed from below, as shown in Figure 10. If rear portion 19 is concave, the concave shape of rear portion 19 may or may not be equal to the concave shape of leading edge portion 18. If the rear portion 19 is not concave, the leading edge portion 18 has a camber forming a concave face on the bottom surface 1 S of the wing 12. The shape of rear portion 19 may be any shape capable of providing aerodynamic lift when coupled to leading edge portion 18. Rear portion 19 may include a riser 21 at the rear portion of wing 12. The riser 21 may form a concave portion on an upper surface 23 of the wing 12 in the rear portion 19. The riser 21 may extend completely across the trailing edge 25 or may extend across only a portion of the trailing edge 25.
In one embodiment, leading edge 18 has a greater thickness than the thickness of the rear portion 19, wherein the characteristic that wing 12 may be bent downwards but not upwards is attributable to the configuration of leading edge portion 18. In other embodiments, leading edge portion 18 and reax portion 19 may or may not have the same thickness, depending on the strength of the materials used to form leading edge portion 18 and rear portion 19.
Wing 12 may have a wing span between about six inches and about twenty four inches. In one embodiment, wing 12 may have a ten inch wing span enabling it to be stored in a cylinder 24, as shown in Figure 3, having a diameter less than three inches. Having the capability of being stored in such small cylinders enables micro air vehicle 10 to be used for reconnaissance missions, for deployment from missiles just prior to impact for bomb damage assessment, and carried by special forces operatives in the field on their person. Micro-air vehicle 10 may be used in other applications as well. In other embodiments, wing 12 may vary in length between about three inches and about 24 inches. As shown in Figures 7 and 9, the micro air vehicle 10 may include a camera 30, wluch may be, but is not limited to being, a video camera, a still photography camera, or other audio or visual recording devices.
The configuration of wing 12 shown in Figures 1-10 and the elastic materials from which the wing 12 is formed enables wing 12 to return to its original, steady state shape, as shown in Figure 1, 4, and 6-10, after being removed from storage without additional steps or use of mechanical mechanisms, such as servos, motors, piezoelectrics, or shape memory alloys. Instead, wing 12 returns to its original shape because of the elastic characteristics of the wing 12 causes the wing 12 to remain under forces when bent from its original position.
These forces abate only when wing 12 is returned to its original position. The materials used to form the wing 12 have great flexibility and elasticity and bend rather than permanently yielding. Thus, micro air vehicle 10 needs only to be removed from a storage container 24, as shown in Figure 3, for wing 12 to return to its original shape.
The wing 12 is configured such that the wing 12 may be bent severely about the body 14 of the micro air vehicle 10. In fact, the wing 12 may be bent so severely that the wing tips 13 and wing 12 are rolled up around the body 14, as shown in Figure 5. This configuration is very advantageous. However, the wing 12 also prevents substantial bending in the opposite direction. This is not to say that the wing will not flex during use. Rather, the wing 12 will flex, or bow, in the opposite direction under normal stresses associated with flight. However, the wing 12 will not bend substantially in the opposite direction.
The configuration of wing 12 possess numerous aerodynamic advantages including:
reduced drag due to the curvature of leading edge portion 18; and improved wind gust rejection due to adaptive washout as a result of wing 12 flexing, twisting and decambering.
This configuration of wing 12 allows micro air vehicle 12 to fly more smoothly than conventional rigid wing designs in smooth and gusty wind conditions. Wing 12 is also more durable than rigid wings because the configuration of wing 12 bends upon impact with the ground or other structure, rather than breaking.
The foregoing is provided for purposes of illustrating, explaining, and describing embodiments of this invention. Modifications and adaptations to these embodiments will be apparent to those skilled in the art and may be made without departing from the scope or spirit of this invention.
Claims (31)
1. A wing for a micro air vehicle, comprising:
at least one layer of a resilient material having a camber forming a concave surface facing downward;
wherein the wing is bendable from a steady state position in a first direction such that tips of the wing may be bent toward the concave surface but not substantially in a second direction that is generally opposite to the first direction; and wherein the wing is capable of returning to the steady state position by releasing the tips of the wing.
at least one layer of a resilient material having a camber forming a concave surface facing downward;
wherein the wing is bendable from a steady state position in a first direction such that tips of the wing may be bent toward the concave surface but not substantially in a second direction that is generally opposite to the first direction; and wherein the wing is capable of returning to the steady state position by releasing the tips of the wing.
2. The wing for a micro air vehicle of claim 1, wherein the at least one layer of a resilient material comprises a leading edge formed from a first material that is different from the material forming a remainder of the at least one layer.
3. The wing for a micro air vehicle of claim 2, wherein the leading edge is formed from an aramid fiber/epoxy mixture and at least a portion of the remainder of the at least one layer is formed from a mixture of carbon fiber and epoxy.
4. The wing for a micro air vehicle of claim 1, wherein the at least one layer of a resilient material is formed from pre-impregnated carbon/epoxy fiber cloth.
5. The wing for a micro air vehicle of claim 1, wherein the at least one layer of a resilient material is formed from an aramid fiber/epoxy mixture.
6. The wing for a micro air vehicle of claim 1, wherein the at least one layer of a resilient material is formed from materials selected from the group consisting of fiber reinforced laminates, sheet metal, foam materials, and plastics.
7. The wing for a micro air vehicle of claim 6, wherein the fiber reinforced laminates are selected from the group consisting of carbon fiber reinforced polymers, glass reinforced polymers, and aramid reinforced polymers.
8. The wing for a micro air vehicle of claim 6, wherein the sheet metal is selected from the group consisting of spring steel, aluminum, stainless steel, and titanium.
9. The wing for a micro air vehicle of claim 1, wherein a wing span of the wing is between about three inches and about twenty four inches.
10. The wing for a micro air vehicle of claim 1, wherein the wing is capable of being bent around a central body of a micro air vehicle so that the micro air vehicle including the wing may fit within a tube having a diameter of about three inches.
11. The wing for a micro air vehicle of claim 1, further comprising a riser section forming a concave portion on an upper surface of the wing proximate to a trailing edge of the wing.
12. A micro air vehicle, comprising:
a central body;
a wing attached to the central body, wherein the wing comprises:
at least one layer of a resilient material having a camber forming a concave surface facing downward;
wherein the wing is bendable from a steady state position in a first direction such that tips of the wing may be bent toward the concave surface but not substantially in a second direction that is generally opposite to the first direction; and wherein the wing is capable of returning to the steady state position by releasing the tips of the wing.
a central body;
a wing attached to the central body, wherein the wing comprises:
at least one layer of a resilient material having a camber forming a concave surface facing downward;
wherein the wing is bendable from a steady state position in a first direction such that tips of the wing may be bent toward the concave surface but not substantially in a second direction that is generally opposite to the first direction; and wherein the wing is capable of returning to the steady state position by releasing the tips of the wing.
13. The micro air vehicle of claim 12, wherein the at least one layer of a resilient material comprises a leading edge formed from a first material that is different from the material forming a remainder of the at least one layer.
14. The micro air vehicle of claim 13, wherein the leading edge is formed from an aramid fiber/epoxy mixture and at least a portion of the remainder of the at least one layer is formed from a mixture of carbon fiber and epoxy.
15. The micro air vehicle of claim 12, wherein the at least one layer of a resilient material is formed from pre-impregnated carbon/epoxy fiber cloth.
16. The micro air vehicle of claim 12, wherein the at least one layer of a resilient material is formed from an aramid fiber/epoxy mixture.
17. The micro air vehicle of claim 12, wherein the at least one layer of a resilient material is formed from materials selected from the group consisting of fiber reinforced laminates, sheet metal, foam materials, and plastics.
18. The micro air vehicle of claim 17, wherein the fiber reinforced laminates are selected from the group consisting of carbon fiber reinforced polymers, glass reinforced polymers, and aramid reinforced polymers.
19. The micro air vehicle of claim 17, wherein the sheet metal is selected from the group consisting of spring steel, aluminum, stainless steel, and titanium.
20. The micro air vehicle of claim 12, wherein a wing span of the wing is between about three inches and about twenty four inches.
21. The micro air vehicle of claim 12, wherein the wing is capable of being bent around a central body of a micro air vehicle so that the micro air vehicle including the wing may fit within a tube having a diameter of about three inches.
22. The micro air vehicle of claim 12, further comprising a riser section forming a concave portion on an upper surface of the wing proximate to a trailing edge of the wing.
23. The micro air vehicle of claim 12, further comprising a tail coupled to the central body that is generally orthogonal to the wing.
24. The micro air vehicle of claim 12, further comprising a tail coupled to the central body that is generally vertical to the wing.
25. A wing for a micro air vehicle, comprising:
a support structure forming an outline of the wing including a leading edge, a trailing edge, and wing tips;
at least one layer of a material attached to the support structure forming a surface of the wing and having a camber forming a concave surface facing downward;
wherein the wing is bendable from a steady state position in a first direction such that tips of the wing may be bent toward the concave surface but not substantially in a second direction that is generally opposite to the first direction; and wherein the wing is capable of returning to the steady state position by releasing the tips of the wing.
a support structure forming an outline of the wing including a leading edge, a trailing edge, and wing tips;
at least one layer of a material attached to the support structure forming a surface of the wing and having a camber forming a concave surface facing downward;
wherein the wing is bendable from a steady state position in a first direction such that tips of the wing may be bent toward the concave surface but not substantially in a second direction that is generally opposite to the first direction; and wherein the wing is capable of returning to the steady state position by releasing the tips of the wing.
26. A wing for a micro air vehicle of claim 25, wherein the support structure is formed from a plurality of ribs.
27. A wing for a micro air vehicle of claim 26, wherein the plurality of ribs are formed from carbon fiber strands.
28. A wing for a micro air vehicle of claim 25, wherein the at least one material is comprised of latex.
29. The wing for a micro air vehicle of claim 25, wherein a wing span of the wing is between about three inches and about twenty four inches.
30. The wing for a micro air vehicle of claim 25, wherein the wing is capable of being bent around a central body of a micro air vehicle so that the micro air vehicle including the wing may fit within a tube having a diameter of about three inches.
31. The wing for a micro air vehicle of claim 25, further comprising a riser section forming a concave portion on an upper surface of the wing proximate to the trailing edge of the wing.
Applications Claiming Priority (3)
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| US60/431,920 | 2002-12-09 | ||
| PCT/US2003/039332 WO2004060743A2 (en) | 2002-12-09 | 2003-12-09 | Bendable wing for micro air vehicle |
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| CA2550146A1 true CA2550146A1 (en) | 2004-07-22 |
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| AU (1) | AU2003302245A1 (en) |
| CA (1) | CA2550146A1 (en) |
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| CN105383683A (en) * | 2015-11-12 | 2016-03-09 | 中国人民解放军国防科学技术大学 | Three-section and impact resisting type UAV (Unmanned Aerial Vehicle) wing |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105383683A (en) * | 2015-11-12 | 2016-03-09 | 中国人民解放军国防科学技术大学 | Three-section and impact resisting type UAV (Unmanned Aerial Vehicle) wing |
| CN105383683B (en) * | 2015-11-12 | 2017-08-18 | 中国人民解放军国防科学技术大学 | A kind of three-stage shock resistance type unmanned plane wing |
Also Published As
| Publication number | Publication date |
|---|---|
| US20060284005A1 (en) | 2006-12-21 |
| AU2003302245A8 (en) | 2004-07-29 |
| US7331546B2 (en) | 2008-02-19 |
| AU2003302245A1 (en) | 2004-07-29 |
| US20040245393A1 (en) | 2004-12-09 |
| WO2004060743A2 (en) | 2004-07-22 |
| WO2004060743A3 (en) | 2005-03-31 |
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Legal Events
| Date | Code | Title | Description |
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| FZDE | Discontinued |